Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 3513 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0068, dated 

March 18, 2014, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2014–1043. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You may 

view this service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on January 

11, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–00993 Filed 1–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0076; Directorate 

Identifier 2013–NM–246–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A330–200, A330–200 

Freighter, and A330–300 series 

airplanes; and Airbus Model A340–200, 

A340–300, A340–500, and A340–600 

series airplanes. This proposed AD was 

prompted by a report that, during a 

production flight test, the ram air 

turbine (RAT) did not pressurize the 

green hydraulic system. For certain 

airplanes, this proposed AD would 

require identification of the part 

number, serial number, and standard of 

the RAT pump, RAT module, RAT 

actuator, and RAT lower gearbox 

assembly; replacement of the balance 

weight screw, modification of the 

actuator coil spring, modification of the 

actuator, an inspection of the anti-stall 

valve for correct installation in the RAT 

pump housing; and corrective actions if 

necessary. For certain other airplanes, 

this proposed AD would require reidentification or replacement of the RAT 

module. We are proposing this AD to 

prevent loss of the impeller function 

and RAT pump pressurization 

capability, which, if preceded by a total 

engine flame-out, could result in the 

loss of control of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 9, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this proposed AD, contact 

Airbus SAS, Airworthiness Office— 

EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 45 

80; email airworthiness.A330A–340@

airbus.com; Internet http://

www.airbus.com. For Hamilton 

Sundstrand service information 

identified in this proposed AD, contact 

Hamilton Sundstrand, Technical 

Publications, Mail Stop 302–9, 4747 

Harrison Avenue, P.O. Box 7002, 

Rockford, IL 61125–7002; telephone 

860–654–3575; fax 860–998–4564; email 

tech.solutions@hs.utc.com; Internet 

http://www.hamiltonsundstrand.com. 

You may view the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425 227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0076; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM 116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–0076; Directorate Identifier 

2013–NM–246–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0274, dated November 

15, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Airbus 

Model A330–200, A330–200 Freighter, 

and A330–300 series airplanes; and 

Airbus Model A340–200, A340–300, 

A340–500, and A340–600 series 

airplanes. The MCAI states: 

During a production flight test of an A330– 

300 aeroplane, the Ram Air Turbine (RAT) 

did not pressurize the green hydraulic 

system. Investigation revealed that the 

impeller drive (hex) shaft had a reduced 

length of engagement with the pump drive 

shaft. This caused the impeller drive shaft to 

disengage from the pump and disconnect the 

impeller. It was determined that the 

disconnection was the result of internal hex 

dimensions on the pump impeller shaft, 

which had been changed in a manufacturing 

drawing. From the investigation analysis, it 

was possible to identify a list of affected 

parts. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
3514 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 

This condition, if not detected and 

corrected, could lead to the loss of impeller 

function and RAT pump pressurization 

capability, possibly resulting, in case of total 

engine flame out, to the loss of control of the 

aeroplane. 

To address this unsafe condition, a new 

design RAT pump shaft has been developed 

with a decreased hexagonal shaft housing 

depth, which increases the hexagonal drive 

shaft engagement in the impeller shaft to 

carry the impeller torque. Airbus issued 

Service Bulletin (SB) A330–29–3122, SB 

A340–29–4093 and SB A340–29–5021 to 

provide instructions for in-service 

replacement of the affected RAT hydraulic 

pumps, or re-identification of the RAT pump 

and complete RAT module, as applicable. 

For the reasons described above, this 

[EASA] AD requires identification and 

replacement [modification] or reidentification of all affected RAT hydraulic 

pumps on A330 and A340–200/300 

aeroplanes, and replacement [modification] 

of all affected RAT modules on A340–500/- 

600 aeroplanes. 

For affected pumps, the required actions 

also include concurrent actions, as 

applicable, including replacement of the 

balance weight screw, modification of 

the actuator coil spring, modification of 

the actuator, an inspection of the antistall valve for correct installation in the 

RAT pump housing and re-installation 

if necessary. For affected pumps, 

corrective actions include replacement 

of the RAT hydraulic pump, and reidentification of the part number of the 

RAT module. You may examine the 

MCAI in the AD docket on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–0076. 

Related ADs 

EASA and the FAA have issued 

additional ADs related to the RAT. FAA 

AD 2012–21–19, Amendment 39–17235 

(77 FR 65812, October 31, 2012), which 

corresponds to EASA AD 2011–0197, 

dated October 10, 2011, requires an 

inspection of the RAT anti-stall valve in 

the pump housing for correct setting, reidentification of the RAT pump, 

performing a functional ground test of 

the RAT, and replacement of the RAT 

pump or the RAT assembly with a 

serviceable part if necessary. FAA AD 

2012–21–19 is applicable to all Airbus 

Model A330–200 freighter series 

airplanes; Model A330–200 and -300 

series airplanes; and Model A340–200 

and -300 series airplanes. 

The FAA also issued AD 2012–21–20, 

Amendment 39–17236 (77 FR 65799, 

October 31, 2012), which corresponds to 

EASA AD 2011–0204, dated October 14, 

2011. FAA AD 2012–21–20 requires 

identification of the supplier, part 

number, and serial number of the RAT 

actuator, and re-identification of the 

RAT actuator and RAT, or replacement 

of the RAT actuator with a serviceable 

unit and re-identification of the RAT, if 

necessary. FAA AD 2012–21–20 is 

applicable to certain Airbus Model 

A330–200 freighter series airplanes, 

Model A330–200 and –300 series 

airplanes, and Model A340–200, –300, 

–500, and –600 series airplanes. 

Related Service Information 

Airbus has issued the following 

service information, which describes 

procedures for modification of the RAT 

pump hex shaft. 

• Airbus Service Bulletin A330–29– 

3122, dated October 25, 2012 (for Model 

A330–200, –200 Freighter, and –300 

series airplanes). 

• Airbus Service Bulletin A340–29– 

4093, dated October 25, 2012 (for Model 

A340–200 and –300 series airplanes). 

• Airbus Service Bulletin A340–29– 

5021, dated October 2, 2012 (for Model 

A340–500 and –600 series airplanes. 

Hamilton Sundstrand has issued 

Service Bulletin ERPS06M–29–19, dated 

August 6, 2012, which describes 

procedures for checking and replacing 

the RAT hydraulic pump. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Clarification of Service Information 

Airbus Service Bulletin A330–29– 

3122, dated October 25, 2012 (for Model 

A330–200, –200 Freighter, and –300 

series airplanes), contains a 

typographical error in the vendor 

service bulletin reference. The Airbus 

service information in some instances 

references Hamilton Sundstrand Service 

Bulletin ‘‘EPRS06M–29–13,’’ but the 

correct reference is ERPS06M–29–19. 

Airbus is aware of the error and plans 

to correct it when Service Bulletin 

A330–29–3122 is revised. 

Costs of Compliance 

We estimate that this proposed AD 

affects 66 airplanes of U.S. registry. 

We also estimate that it would take 

about 14 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $78,540, or $1,190 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

up to 18 work-hours and require parts 

costing up to $427,301, for a cost of 

$428,831 per product. We have no way 

of determining the number of aircraft 

that might need this action. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 3515 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2015–0076; 

Directorate Identifier 2013–NM–246–AD. 

(a) Comments Due Date 

We must receive comments by March 9, 

2015. 

(b) Affected ADs 

This AD affects AD 2012–21–19, 

Amendment 39–17235 (77 FR 65812, October 

31, 2012); and AD 2012–21–20, Amendment 

39–17236 (77 FR 65799, October 31, 2012). 

(c) Applicability 

This AD applies to all airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category, all manufacturer 

serial numbers. 

(1) Airbus Model A330–201, –202, –203, 

–223, –223F, –243, –243F, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes. 

(2) Airbus Model A340–211, –212, –213, 

–311, –312, –313, –541, and –642 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29, Hydraulic Power. 

(e) Reason 

This AD was prompted by a report that, 

during a production flight test, the ram air 

turbine (RAT) did not pressurize the green 

hydraulic system. We are issuing this AD to 

prevent loss of the impeller function and 

RAT pump pressurization capability, which, 

if preceded by a total engine flame-out, could 

result in the loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Identification of RAT Components 

For Airbus Model A330–201, –202, –203, 

–223, –223F, –243, –243F, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes; and Model A340–211, –212, –213, 

–311, –312, and –313 airplanes: Except as 

provided by paragraph (i) of this AD, within 

36 months after the effective date of this AD, 

identify the part number, serial number, and 

standard (through the mod-dots) of the RAT 

pump, RAT module, RAT actuator, and RAT 

lower gearbox assembly, in accordance with 

the Accomplishment Instructions of the 

applicable Airbus service information 

specified in paragraphs (g)(1) and (g)(2) of 

this AD. A review of airplane maintenance 

records is acceptable in lieu of this 

identification if the part number, serial 

number, and standard can be conclusively 

determined from that review. 

(1) For Airbus Model A330–201, –202, 

–203, –223, –223F, –243, –243F, –301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes: Airbus Service Bulletin A330–29– 

3122, dated October 25, 2012. 

(2) For Airbus Model A340–211, –212, 

–213, –311, –312, and –313 airplanes: Airbus 

Service Bulletin A340–29–4093, dated 

October 25, 2012. 

(h) Corrective and Concurrent Actions 

If the serial number of the RAT hydraulic 

pump is included in table 7, ‘‘Suspect 

Hydraulic Pump Serial Numbers,’’ of 

Hamilton Sundstrand Service Bulletin 

ERPS06M–29–19, dated August 6, 2012: 

Within 36 months after the effective date of 

this AD, do all applicable corrective actions, 

in accordance with the Accomplishment 

Instructions of the applicable Airbus service 

information specified in paragraphs (g)(1) 

and (g)(2) of this AD. Prior to or concurrently 

with doing the corrective actions required by 

this paragraph, do the actions specified in 

paragraphs (h)(1) through (h)(4) of this AD, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

29–3122, dated October 25, 2012 (for Model 

A330–200, –200 Freighter, and –300 series 

airplanes); or Airbus Service Bulletin A340– 

29–4093, dated October 25, 2012 (for Airbus 

Model A340–211, –212, –213, –311, –312, 

and –313 airplanes). 

(1) Replace the balance weight screw. 

(2) Modify the actuator coil spring. 

(3) Modify the actuator. 

(4) Do a general visual inspection of the 

anti-stall valve for correct installation in the 

RAT pump housing, and if any incorrect 

installation is found, before further flight, 

correctly install the anti-stall valve. 

(i) Exception to Service Information 

Specifications 

Where Airbus Service Bulletin A330–29– 

3122, dated October 25, 2012 (for Model 

A330–200, –200 Freighter, and –300 series 

airplanes), refers to Hamilton Sundstrand 

Service Bulletin ‘‘EPRS06M–29–13’’ as an 

additional source of guidance for doing 

certain actions required by paragraph (h) of 

this AD, the correct reference should be to 

Hamilton Sundstrand Service Bulletin 

ERPS06M–29–19. 

(j) Re-identification of Part Numbers 

If the serial number of the RAT hydraulic 

pump is not included in table 7, ‘‘Suspect 

Hydraulic Pump Serial Numbers,’’ of 

Hamilton Sundstrand Service Bulletin 

ERPS06M–29–19, dated August 6, 2012: 

Within 36 months after the effective date of 

this AD, re-identify the part numbers of the 

RAT hydraulic pump and RAT module, in 

accordance with the Accomplishment 

Instructions of the applicable Airbus service 

information specified in paragraphs (g)(1) 

and (g)(2) of this AD. 

(k) RAT Module Replacement (Modification) 

For Airbus Model A340–541 and –642 

airplanes having RAT module P/N 772722D, 

772722E, 772722F, or 772722G: Within 36 

months after the effective date of this AD, 

replace (modify) the RAT module, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A340– 

29–5021, dated October 2, 2012. 

(l) Exception to Paragraphs (g), (h), and (j) 

of This AD 

The actions required by paragraph (g), (h) 

and (j) of this AD are not required for 

airplanes on which Airbus Modification 

202537 was embodied in production, 

provided it can be determined that, since the 

airplane’s first flight, no RAT hydraulic 

pump or RAT module having a part number 

identified in paragraph (n) of this AD is 

installed on that airplane. 

(m) Terminating Action for Certain 

Requirements of Other ADs 

(1) For Airbus Model A330–201, –202, 

–203, –223, –223F, –243, –243F, –301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes; and A340–211, –212, –213, –311, 

–312, and –313 airplanes: Accomplishment 

of the actions required by paragraphs (g), (h), 

and (j) of this AD constitutes compliance 

with the requirements of paragraphs (g)(1) 

and (g)(2) of AD 2012–21–19, Amendment 

39–17235 (77 FR 65812, October 31, 2012); 

and paragraphs (g)(1) and (g)(2) of AD 2012– 

21–20, Amendment 39–17236 (77 FR 65799, 

October 31, 2012). 

(2) For Airbus Model A340–541 and –642 

airplanes: Accomplishment of the actions 

required by paragraph (k) of this AD 

constitutes compliance with the 

requirements of paragraphs (h)(1) and (h)(2) 

of AD 2012–21–20, Amendment 39–17236 

(77 FR 65799, October 31, 2012). 

(n) Parts Installation Prohibition 

(1) For Airbus Model A330–201, –202, 

–203, –223, –223F, –243, –243F, –301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes; and A340–211, –212, –213, –311, 

–312, and –313 airplanes: After modification 

of the RAT module as required by paragraph 

(h) of this AD, no person may install any 

complete RAT module having a part number 

(P/N) identified in paragraph (n)(1)(i) of this 

AD, or any RAT hydraulic pump having the 

part number identified in paragraph (n)(1)(ii) 

of this AD, on any airplane. 

(i) RAT module P/N 766351, 768084, 

770379, 770952, 770952A, 770952B, 

1702934, 1702934A, or 1702934B. 

(ii) RAT hydraulic pump P/N 5909522 

(Parker P/N 4207902). 

(2) For Airbus Model A340–541 and –642 

airplanes: After modification of the RAT 

module as required by paragraph (k) of this 

AD, no person may install any complete RAT 

module having P/N 772722D, 772722E, 

772722F, or 772722G, on any airplane. 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 


emcdonald on DSK67QTVN1PROD with PROPOSALS
3516 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM 116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0274, dated 

November 15, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–0076. 

(2) For Airbus service information 

identified in this AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 45 80; email airworthiness.A330- 

A340@airbus.com; Internet http://

www.airbus.com. For Hamilton Sundstrand 

service information identified in this AD, 

contact Hamilton Sundstrand, Technical 

Publications, Mail Stop 302–9, 4747 Harrison 

Avenue, P.O. Box 7002, Rockford, IL 61125– 

7002; telephone 860–654–3575; fax 860–998– 

4564; email tech.solutions@hs.utc.com; 

Internet http://

www.hamiltonsundstrand.com. You may 

view the referenced service information at 

the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on January 

14, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–00961 Filed 1–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1044; Directorate 

Identifier 2014–NM–148–AD] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Cessna Aircraft Company Model 500, 

501, 550, 551, S550, 560, and 650 

airplanes. This proposed AD was 

prompted by reports of smoke and/or 

fire in the tailcone caused by sparking 

due to excessive wear of the brushes in 

the air conditioning (A/C) motor. This 

proposed AD would require inspections 

to determine if certain A/C compressor 

motors are installed and to determine 

the accumulated hours on certain A/C 

compressor motor assemblies; and 

repetitive replacement of the brushes in 

the A/C compressor motor assembly, or, 

as an option to the brush replacement, 

deactivation of the A/C system and 

placard installation; and return of 

replaced brushes to Cessna. We are 

proposing this AD to prevent the 

brushes in the A/C motor from wearing 

down beyond their limits, which could 

result in the rivet in the brush 

contacting the commutator, causing 

sparks and consequent fire and/or 

smoke in the tailcone with no means to 

detect or extinguish the fire and/or 

smoke. 

DATES: We must receive comments on 

this proposed AD by March 9, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Cessna 

Aircraft Co., P.O. Box 7706, Wichita, KS 

67277; telephone 316–517–6215; fax 

316–517–5802; email citationpubs@

cessna.textron.com; Internet https://

www.cessnasupport.com/newlogin.html. 

You may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

1044; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Craig Henrichsen, Aerospace Engineer, 

Electrical Systems and Avionics Branch, 

ACE–119W, FAA, Wichita Aircraft 

Certification Office (ACO), 1801 Airport 

Road, Room 100, Mid-Continent 

Airport, Wichita, KS 67209; phone: 

316–946–4110; fax: 316–946–4107; 

email: Craig.Henrichsen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA–

2014–1044; Directorate Identifier 2014– 

NM–148–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received reports of smoke/

fire (three reports of fire) in the tailcone 

of Cessna Aircraft Company Model 525, 

550, and 560 airplanes, where 

investigation revealed brushes had worn 


emcdonald on DSK67QTVN1PROD with PROPOSALS